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NREL's S804 Airfoil (s804-nr) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S804 Airfoil (s804-nr)
Reynolds number: 100,000
Max Cl/Cd: 28.56 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s804-nr-100000.txt
Download as CSV file: xf-s804-nr-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S804 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2756   0.10803   0.10389  -0.0383   1.0000   0.1580
  -9.000  -0.2709   0.10693   0.10290  -0.0351   0.9985   0.1596
  -8.750  -0.4679   0.06059   0.05561  -0.0872   0.9601   0.0820
  -8.500  -0.4410   0.05532   0.05025  -0.0918   0.9483   0.0812
  -8.250  -0.4197   0.04950   0.04409  -0.0975   0.9349   0.0797
  -8.000  -0.3959   0.04373   0.03775  -0.1033   0.9221   0.0783
  -7.750  -0.3583   0.03892   0.03233  -0.1091   0.9138   0.0788
  -7.500  -0.3233   0.03557   0.02832  -0.1129   0.9009   0.0813
  -7.250  -0.2788   0.03249   0.02495  -0.1170   0.8920   0.0838
  -7.000  -0.2365   0.03029   0.02262  -0.1197   0.8803   0.0867
  -6.750  -0.1973   0.02852   0.02043  -0.1220   0.8658   0.0913
  -6.500  -0.1580   0.02673   0.01870  -0.1239   0.8519   0.0962
  -6.250  -0.1174   0.02531   0.01699  -0.1258   0.8378   0.1022
  -6.000  -0.0816   0.02402   0.01580  -0.1269   0.8225   0.1104
  -5.750  -0.0534   0.02302   0.01482  -0.1267   0.8048   0.1189
  -5.500  -0.0272   0.02219   0.01403  -0.1262   0.7876   0.1320
  -5.250  -0.0017   0.02134   0.01327  -0.1258   0.7715   0.1541
  -5.000   0.0241   0.02009   0.01233  -0.1262   0.7571   0.2042
  -4.750   0.0508   0.01870   0.01168  -0.1274   0.7429   0.3241
  -4.500   0.0766   0.01907   0.01228  -0.1265   0.7277   0.4150
  -4.250   0.1036   0.01990   0.01301  -0.1252   0.7147   0.4592
  -4.000   0.1305   0.02074   0.01368  -0.1239   0.7021   0.4931
  -3.750   0.1527   0.02163   0.01456  -0.1213   0.6891   0.5153
  -3.500   0.1792   0.02233   0.01508  -0.1196   0.6789   0.5356
  -3.250   0.1981   0.02307   0.01587  -0.1164   0.6665   0.5487
  -3.000   0.2235   0.02362   0.01625  -0.1145   0.6576   0.5642
  -2.750   0.2452   0.02397   0.01655  -0.1129   0.6463   0.5802
  -2.500   0.2697   0.02443   0.01687  -0.1109   0.6384   0.5935
  -2.250   0.2896   0.02476   0.01720  -0.1087   0.6286   0.6051
  -2.000   0.3175   0.02485   0.01708  -0.1087   0.6202   0.6203
  -1.750   0.3367   0.02521   0.01743  -0.1058   0.6124   0.6287
  -1.500   0.3631   0.02522   0.01733  -0.1059   0.6037   0.6419
  -1.250   0.3864   0.02542   0.01739  -0.1040   0.5975   0.6502
  -1.000   0.4126   0.02548   0.01740  -0.1045   0.5896   0.6620
  -0.750   0.4329   0.02564   0.01755  -0.1024   0.5830   0.6690
  -0.500   0.4667   0.02564   0.01730  -0.1042   0.5775   0.6802
  -0.250   0.4858   0.02584   0.01756  -0.1023   0.5714   0.6862
   0.000   0.5096   0.02599   0.01769  -0.1018   0.5648   0.6940
   0.250   0.5414   0.02597   0.01752  -0.1031   0.5594   0.7023
   0.500   0.5663   0.02614   0.01759  -0.1023   0.5548   0.7082
   0.750   0.5890   0.02642   0.01795  -0.1021   0.5486   0.7153
   1.000   0.6174   0.02660   0.01808  -0.1029   0.5434   0.7223
   1.250   0.6426   0.02675   0.01817  -0.1023   0.5394   0.7279
   1.500   0.6742   0.02698   0.01826  -0.1033   0.5359   0.7346
   1.750   0.6964   0.02752   0.01891  -0.1034   0.5309   0.7414
   2.000   0.7168   0.02791   0.01937  -0.1024   0.5261   0.7469
   2.250   0.7440   0.02819   0.01962  -0.1027   0.5219   0.7532
   2.500   0.7762   0.02842   0.01974  -0.1040   0.5184   0.7604
   2.750   0.8015   0.02882   0.02010  -0.1036   0.5155   0.7667
   3.000   0.8172   0.02977   0.02126  -0.1027   0.5111   0.7738
   3.250   0.8374   0.03060   0.02218  -0.1025   0.5072   0.7804
   3.500   0.8578   0.03121   0.02285  -0.1017   0.5038   0.7875
   3.750   0.8871   0.03166   0.02327  -0.1025   0.5006   0.7965
   4.000   0.9123   0.03194   0.02353  -0.1020   0.4980   0.8042
   4.250   0.9362   0.03288   0.02449  -0.1023   0.4949   0.8135
   4.500   0.9333   0.03483   0.02675  -0.0991   0.4907   0.8211
   4.750   0.9395   0.03674   0.02884  -0.0977   0.4869   0.8311
   5.000   0.9492   0.03803   0.03023  -0.0959   0.4836   0.8415
   5.250   0.9721   0.03853   0.03075  -0.0953   0.4810   0.8538
   5.500   1.0041   0.03856   0.03073  -0.0956   0.4788   0.8677
   5.750   1.0334   0.03896   0.03110  -0.0958   0.4769   0.8834
   6.000   0.5302   0.09126   0.08464  -0.0922   0.5269   0.8582
   6.250   0.5516   0.09268   0.08609  -0.0922   0.5212   0.8759
   6.500   0.5816   0.09426   0.08772  -0.0924   0.5183   0.9012
   7.750   0.6397   0.10648   0.10000  -0.0992   0.4832   1.0000
   8.000   0.6790   0.10884   0.10229  -0.1011   0.4793   1.0000
   8.250   0.7271   0.11192   0.10532  -0.1031   0.4773   1.0000
   8.500   0.6855   0.11432   0.10777  -0.1028   0.4635   1.0000
   8.750   0.7236   0.11662   0.11003  -0.1039   0.4597   1.0000
   9.000   0.7738   0.11979   0.11315  -0.1052   0.4578   1.0000
   9.250   0.7268   0.12207   0.11549  -0.1052   0.4435   1.0000
   9.500   0.7675   0.12446   0.11786  -0.1059   0.4401   1.0000
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